CN103899419B - The method of operation of axial flow compressor and axial flow compressor - Google Patents
The method of operation of axial flow compressor and axial flow compressor Download PDFInfo
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- CN103899419B CN103899419B CN201310534353.5A CN201310534353A CN103899419B CN 103899419 B CN103899419 B CN 103899419B CN 201310534353 A CN201310534353 A CN 201310534353A CN 103899419 B CN103899419 B CN 103899419B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
- F02C3/305—Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
- F02C7/1435—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages by water injection
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/306—Mass flow
- F05D2270/3062—Mass flow of the auxiliary fluid for heating or cooling purposes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/502—Thermal properties
- F05D2300/5021—Expansivity
- F05D2300/50212—Expansivity dissimilar
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
The invention provides the method for operation of a kind of axial flow compressor and axial flow compressor, when the specified running of axial flow compressor with the cooling during rolling effect to air-breathing spray droplet, suppress the gap shrinks between intergrade moving vane front end and inner walls face, excellent in reliability.A kind of gas turbine axial flow compressor, possesses the unit of the action fluid supply drop before compression or in compression, and there are multiple levels that the mode of evaporating in above-mentioned compressor with above-mentioned drop formed, above-mentioned gas turbine axial flow compressor has cavity on the housing of above-mentioned compressor, this cavity by above-mentioned housing and surround above-mentioned compressor multistage moving vane surrounding and is formed in inside and compresses side body in runner and form, and possess the runner that the pressurized air than above-mentioned cavity side farther downstream can be supplied to above-mentioned cavity.
Description
Technical field
The present invention relates to the gas turbine with air-breathing spraying with or the axial flow compressor of production and method of operation thereof.
Background technique
Such as, in the running of the gas turbine in summer etc., because of temperature high when air-breathing density low and the output of gas turbine is declined.This output is reduced, such as, exists and make air-breathing density increase by the drop of the suction air-atomizing water to compressor etc., and improve the method for gas turbine output by the effect that air-breathing cools.Further, when making the spray amount of this drop increase and to import drop to compressor inside, make compression power decline with the efficiency improving gas turbine by intercooled effect.Be transported to the small drop of compressor inside together with this air-flow while between being arranged by moving vane, stator blade arrange between while be evaporated to the saturation temperature of level, under the effect of its latent heat of vaporization, make the temperature of action fluid reduce.
Because drop gasifies and makes main flow temperature decline from the upstream side of compressor in multistage axial flow compressor, thus formed from swim on the compressor side rows of blades load reduction and the downstream side rows of blades load of its opposition side increase, distribute relative to the common operating load of flow direction different distributions.Usually, in the partial load running of gas turbine, because upstream side is compared in the rows of blades load in compressor downstream side become large, if so partial load time spray droplet, downstream side rows of blades load is increased further, therefore there is the possibility making rows of blades reliability decrease.Therefore, when the spraying of drop starts from the steady running of gas turbine arrival rated load.
In addition, within the compressor, gap between the internal face of housing and the peripheral part of moving vane changes under the effect of rotor and the thermal expansion difference between moving vane and housing, if the thermal expansion of housing is larger than rotor, the gap of moving vane front end becomes large and the efficiency of compressor is significantly declined.On the contrary, if the thermal expansion of rotor, moving vane is larger than the thermal expansion of housing too many, moving vane contacts with inner walls face and likely damages moving vane front end.In general simple cycle gas turbine engine compressor, when considering this thermal expansion difference and moving vane front space be set as being most suitable for specified running.But, spraying a large amount of drop and carry out in intercooled compressor to the air-breathing of gas turbine, due to spray droplet during specified running, therefore produce thermal distortion and the complete different phenomenon of general simple cycle gas turbine engine of housing.
In the control of the moving vane front space of simple cycle gas turbine engine, because the housing of compressor and the thermal expansion difference of rotor and moving vane reach maximum at the high-temperature area of the downstream stage of compressor, therefore as the control structure of this moving vane front space, such as, there is the control structure shown in patent documentation 1.In patent documentation 1, side body in compressor is compared and is around cooled by the pumped air disclosed by bleeding by the intergrade from compressor, thus the axial temperature gradient of compressor is diminished, control the technology in the gap between inner walls face and moving vane front end.
Patent documentation
Patent documentation 1: Japanese Unexamined Patent Publication 2004-3492 publication
The thermal distortion of housing when thermal distortion and a large amount of drop of spraying of compressor housing during the specified running of the simple cycle gas turbine engine described in above-mentioned technology carry out the specified running of intercooled compressor has relatively big difference, is described its difference.
First, in simple cycle gas turbine engine, flow through the temperature of the main flow of compressor inside under the effect of the enthalpy increase caused because of compression, rear-stage side compares the high temperature that preceding-stage side (being probably atmospheric temperature) reaches about 400 DEG C ~ 450 DEG C.Thus, the rear-stage side of housing compares preceding-stage side thermal expansion change greatly.On the other hand, to sucking in the compressor of air-atomizing a large amount of drop because relative to the flow direction of compressor from upstream side at intergrade droplets pack in housing, so housing is cooled sharp, suppress the thermal expansion of the housing of intergrade.Thus, there is the possibility that the thermal expansion of rotor or moving vane is larger than the thermal expansion of housing.Because the rear-stage side drop at compressor evaporates completely, therefore housing is adhered to by drop and cooled possibility is lower.
Thus, in the technology of patent documentation 1, owing to not considering the axial flow compressor of the cooling during rolling effect of the air-breathing spray droplet had compressor, therefore when carrying out air-breathing spraying, in the intergrade of compressor,, there is moving vane front end and contact with inner walls face and make the danger that moving vane front end damages in the gap smaller between moving vane front end and the internal face of housing.
Summary of the invention
The object of the present invention is to provide a kind of axial flow compressor and method of operation thereof, when having the specified running to the axial flow compressor of air-breathing spray droplet, suppressing the gap shrinks between intergrade moving vane front end and inner walls face, excellent in reliability.
For achieving the above object, the action fluid that axial flow compressor of the present invention possesses to compressor supplies the drop feed unit of drop and forms the housing of the runner flowed down for above-mentioned stream of action body, and there is multiple to be arranged by continuous print moving vane and a moving vane arranges the level formed, above-mentioned drop evaporates in above-mentioned compressor, the feature of this axial flow compressor is, above-mentioned housing has cavity, above-mentioned cavity is by outside housing and surround surrounding that multistage moving vane arranges and side body is formed in the runner that inside forms above-mentioned action fluid, possesses the runner for the above-mentioned action fluid of side farther downstream, the region of the above-mentioned cavity of formation than above-mentioned interior side body being supplied to above-mentioned cavity.
Effect of the present invention is as follows.
According to the present invention, a kind of axial flow compressor and method of operation thereof can be provided, when running specified to the axial flow compressor of air-breathing spray droplet, suppress the gap shrinks between intergrade moving vane front end and inner walls face, excellent in reliability.
Accompanying drawing explanation
Fig. 1 is the pie graph possessing the gas turbine engine systems of air-breathing spraying of one of embodiments of the present invention.
Fig. 2 is the meridian plane sectional view of the axial flow compressor of one of embodiments of the present invention.
Fig. 3 is the meridian plane sectional view of the axial flow compressor of one of embodiments of the present invention.
Fig. 4 is the meridian plane sectional view of the axial flow compressor of one of embodiments of the present invention.
Fig. 5 is the control system pie graph of one of embodiments of the present invention.
Fig. 6 is the control system pie graph of one of embodiments of the present invention.
In figure: 1-compressor, 2-burner, 3-turbo machine, 4-generator, 5-running shaft, 11-air, 12-high-pressure air, 13-fuel, 14-high-temperature combustion gas, 15-exhaust, 31-aspirating air pipe, 32-spraying nozzle, 33-air-breathing static pressure box, 51-moving vane arranges, 52-rotor, 53-stator blade arranges, 54-housing, 55-inlet guide vane, 56-variable stator blade mechanism, 57-intergrade moving vane arranges, 61-moving vane front end, 62-outside circular shell, 63-inner annular housing, 64, 65-cavity, 71-cooling-air is bled pipe arrangement, 72, 73, 74-high temperature, high-pressure air supply passage, 81, 82-valve, 83-moving vane front space measuring transducer, 84-controller, 85-sensor for measuring temperature, 91, 92-transceiver channel.
Embodiment
Fig. 1 summarily represents the overall pie graph of the gas turbine engine systems possessing air-breathing spraying.Below, the configuration example of Fig. 1 to the gas turbine engine systems possessing air-breathing spraying is used to be described.
Gas turbine engine systems by air compressing is generated high-pressure air compressor 1, make pressurized air and fuel mix and the burner 2 of burning and being formed by the turbo machine 3 that the combustion gas of high temperature carry out rotary actuation.Compressor 1 is connected with generator 4 by running shaft 5 with turbo machine 3.
Next, the flowing of action fluid is described.Air 11 as action fluid flows into compressor 1, by compressor compresses while flow into burner 2 as high-pressure air 12.In burner 2, make high-pressure air 12 and fuel 13 mix combining combustion, generate the combustion gas 14 of high temperature.Combustion gas 14 are discharged outside system as waste gas 15 after turbo machine 3 is rotated.Generator 4 is transmitted the turbo machine come rotating power by the running shaft 5 by connecting compressor and turbo machine drives.
The volume flowrate that gas turbine engine systems is general used certain determine in revolution compressor, when the inhalation temperatures such as summer are high, make the mass flow rate of suction air reduce because air density diminishes, therefore corresponding, also have to reduce at the fuel flow rate of burner combustion.That is, the inhalation temperature that there is compressor more uprises, and the problem declined is got in the output of gas turbine.
Therefore, there is the method under the effect effect of the air-breathing cooling of the drop by the air-breathing spray water to compressor etc., gas turbine output being improved.As air-breathing cooling method, exist and medium formula air-breathing cooler be set on aspirating air pipe, and by suck air through air-breathing cooler with the method making inhalation temperature decline.On the other hand, also there is configuring spraying droplets mouth 32 and make it evaporate method inhalation temperature being declined by the latent heat of vaporization of drop in the gas flow by fine droplet of spraying in air-breathing in aspirating air pipe 31 as shown in Figure 1.
When using such method of spraying to drop, except increase drop amount and drop evaporate and obtain air-breathing cooling effect in aspirating air pipe, drop can also be supplied to compressor inside, and can expect to obtain cooling during rolling effect by drop at compressor internal gasifier.Accordingly, the high efficiency of the gas turbine reducing and obtain because of the output raising of gas turbine and compression power can be contributed to.In addition, in the present embodiment, although only illustrate the position that spraying droplets mouth 32 is located at aspirating air pipe 31, also at air-breathing static pressure box 33 two benches of aspirating air pipe 31 and suction port of compressor, spraying nozzle can be set respectively.
Use the synoptic diagram in the meridian plane cross section of the compressor of Fig. 2, the detailed configuration of compressor is described.Axial flow compressor 1 is made up of with the housing 54 being provided with multiple stator blade row 53 rotor 52 of the rotation being provided with multiple moving vane row 51, and forms annular runner by the outer circumferential face of rotor 52 and the inner peripheral surface of housing 54.Moving vane row 51 and stator blade row 53 are alternately configuration vertically, moving vane row and stator blade row formation level.Be provided with at the upstream side of elementary moving vane and control inhalation flow and the inlet guide vane (IGV) 55 that can adjust gas turbine load.In addition, preceding-stage side stator blade row possesses changeable mechanism 56 in order to rotating stall when suppressing gas turbine to start.Although the stator blade row possessing changeable mechanism in Fig. 2 are only elementary stator blade, also there is the situation possessing multistage variable stator blade.
90 degree are turned to and to compressor internal feed at the air-breathing static pressure box 33 being positioned at upstream of compressor side from aspirating air pipe (not shown) leaked-in air 11.The drop of water etc. sprays from the spraying nozzle 32 being disposed in aspirating air pipe inside, and small drop evaporates in the gas flow, by its latent heat of vaporization, the gas temperature of inflow compressor is declined, and meanwhile, makes the density of air-breathing increase.Not being fully vaporized prior to saturated drop at air-breathing static pressure box in the fine droplet be together transferred with air-flow keeps the state of drop to flow into compressor inside.
Drop in the inside of compressor while between being arranged by moving vane, stator blade row between while be evaporated to saturation temperature, the temperature of the action fluid in compression process is declined.Owing to making compression property close to isothermal compression by this cooling during rolling effect, therefore, it is possible to reduce the power of compressor.Ideal situation is, all drops being imported into compressor evaporate completely in the gas flow before being discharged by compressor.But the part that there is the drop sprayed from spraying nozzle does not help the cooling of primary air but piles up, is discharged to as draining the situation of compressor outside as liquid film.
Next, the drop action of the primary air being helpless to compressor is described, as mentioned above, sometimes collides with the wall of air-breathing static pressure box 33 in a part for the drop of aspirating air pipe internal spraying and pile up as liquid film.In addition, when drop after spraying interferes with each other and generates the larger drop of particle diameter, this drop together can not be transferred with air-flow and and collision with wall, pile up as liquid film.Further, collide with the strut 58 of entrance or IGV55 that are positioned at compressor, its part is attached to blade surface and forms liquid film.The division of this liquid film of a part, forms the large secondary drop of particle diameter and flows into compressor inside.In the inside of compressor, the drop that particle diameter is large and moving vane 51 collide and are blown under the centrifugal action rotated at moving vane and fly to outer circumferential side and form liquid film on inner walls face.
Part liquid film evaporates under the heat conducting effect of housing, and remaining is again separated formation secondary drop and flies to downstream stage.Particle diameter due to this secondary drop becomes large, therefore collides with the rotor and stator blade in downstream and the possibility forming liquid film uprises.The scope that such liquid film exists be from the most prime of axial flow compressor to the level (terminating level hereinafter referred to as evaporation) that drop evaporates completely in compressor inside, especially, confirm to produce liquid film in intergrade from upstream side.In addition, the main flow temperature that evaporation terminates near level is more than 300 DEG C, even if thinking that drop and inner walls face are collided also can flash evapn.
Next, compressor blade front space is described.Within the compressor, gap between the internal face of housing and the peripheral part of moving vane changes under the effect of rotor and the thermal expansion difference between moving vane and housing, if the thermal expansion of housing is comparatively large, the gap of moving vane front end becomes large and the efficiency of compressor is significantly declined.On the other hand, if the thermal expansion of rotor, moving vane is larger than the thermal expansion of housing too many, there is moving vane and contact with inner walls face and damage the possibility of moving vane front end.This phenomenon becomes the most serious when the specified running of gas turbine.Owing to being mainly out of shape under centrifugal action relative to the rotor of preceding-stage side and moving vane, thermal distortion under rear-stage side is the effect in centrifugal force and thermal expansion, therefore the thermal expansion difference of rotor and moving vane and housing prediction raising compressor efficiency with guarantee it is important in reliability.
In the compressor of general simple cycle gas turbine engine, under the effect that the temperature of the main flow of internal flow increases at the enthalpy that caused by compression, its grade of side is than high about 400 DEG C ~ 450 DEG C of preceding-stage side (being probably atmospheric temperature).Therefore the rear-stage side of housing becomes large than preceding-stage side thermal expansion.Consider this thermal expansion difference by vane nose gap design for being most suitable for specified running time.But the mode due to the in fact thermal distortion of housing is that more high temperature is more complicated for main flow temperature, is therefore difficult to the vane nose gap setting rear-stage side accurately.Therefore, in the compressor of simple cycle gas turbine engine, the aspirating chamber as cavity being also set in the housing of rear-stage side, cooling the housing in downstream side to control vane nose gap by using this pumped air.
On the other hand, carry out in intercooled compressor at a large amount of drop of spraying to the air-breathing of gas turbine, the inner walls face from preceding-stage side to intergrade forms liquid film.Because the temperature of primary air slowly rises, so the thermal distortion of liquid film to housing being piled up in preceding-stage side almost has no impact along with flowing from atmospheric temperature.But terminate level by the intergrade of upstream side than the evaporation of drop being positioned at, the inner walls face of high temperature is attached with the thermal distortion of drop on housing larger impact.
During specified running before spray droplet, to intergrade moving vane front end and surround between the inner walls face of the ring-type of this moving vane, there is certain gap state under, be described during spray droplet.When the housing accumulation of intergrade has drop and forms liquid film, by heat transfer, case temperature is declined, suppress the thermal expansion of housing.Therefore the thermal expansion of housing makes than the thermal expansion of rotor, moving vane and makes the gap shrinks in moving vane and inner walls face.Then, when the thermal expansion of housing becomes too small, there is the possibility that moving vane contacts with inner walls face, moving vane front end is damaged.
On the other hand, when being designed significantly by moving vane front space in the spraying considering drop, vane nose gap can be made to be minimum to suppress the thermal distortion of housing by the spray droplet when high temperature.But, because spraying droplets during low temperature is adjusted to small flow or stopping, therefore being made the decrease in efficiency of compressor by the expansion of moving vane front space.In addition, due to the steam output change in aspirating air pipe under the inhalation temperature, damp condition effect of compressor, therefore the evaporation position of compressor inside also changes.That is, because evaporation terminates level due to air conditions, spray amount and changing, be therefore difficult to set the gap value between moving vane front end exactly during design.In addition, when carrying out air-breathing spraying when the operating temperature of compressor operates than partial load low during specified running, although it is more than needed to make moving vane front space have owing to suppressing the thermal expansion of rotor and moving vane, but the inlet guide vane of compressor (IGV) is than compared with during specified running, be in closed condition, drop and IGV collide and make water displacement increase and can not obtain effective cooling during rolling effect, moreover likely produce acid etching impact to moving vane.
The compressor of Fig. 2 to the first embodiment of the present invention is used to be described.In the present embodiment, be formed with at the housing of the intergrade (terminating level upstream side than the evaporation of drop) of axial flow compressor the cavity 64 be along the circumferential direction communicated with.In addition, the same cavity 65 be along the circumferential direction communicated with is formed in the downstream side of cavity 64.Then, cavity 64 is by being formed in inside and compress the double housing that the inner annular housing 63 of runner forms and formed around the intergrade moving vane 57 comprising outside circular shell 62 and surround compressor.Then, possess and can will flow through the runner 72 supplied than the cavity 64 of a compressed-air actuated part upstream side of the high temperature of side, high pressure farther downstream, region of the formation cavity 64 of inner circumferential side circular shell 63 from cavity 65.Also in the runner 72 that upstream side cavity 64 supplies high temperature, high-pressure air, the valve etc. that can control flow can be set at this.
Next, when spraying droplets being carried out on the present embodiment, the impact of moving vane front space is described.As shown in Figure 2, when intergrade along the circumferential direction arranges cavity relative to radial direction as two different double housing structures, be attached on inner annular housing 63 by drop and suppress thermal expansion.But, on the outside circular shell 62 being provided with inner annular housing 63, compared with when cavity 64 is not set, thermal capacity diminishes, do not adhere to drop in addition, therefore the effect of thermal expansion is suppressed to reduce, because inner annular housing 63 is supported on outside circular shell 62, so inner annular housing 62 also radially moves with the hot elongation of outer ring shape housing 62.Therefore, it is possible to suppress reducing of the gap of moving vane front end 61.
Have again, by by from the high temperature of downstream stage cavity 65, the pressurized gas of high pressure by runner 72 upstream side cavity 64 supply, warming-up is carried out to outer ring shape housing 62 and the temperature in cavity is controlled in setting value, thus can control thermal expansion, therefore, it is possible to suppress reducing of the gap of moving vane front end 61.In addition, by making inner annular housing 63 at higher temperature, the drop being attached to inner annular housing 63 inner circumferential side can be made to evaporate and suppress the generation of draining.In addition, when the valve of the compressed air require being supplied to upstream side cavity 64 can be controlled in runner 72 setting, more effectively can control the temperature in cavity 64, gap control or suppression can be made to produce the more remarkable effect of draining.
In addition, with regard to the material of outside circular shell 62 and inner annular housing 63, it is effective that inner annular housing 63 uses the material low compared to outside housing linear expansion coeffcient to make housing.Thermal expansion amount calculates according to the long-pending of the linear expansion coeffcient of thickness of shell, length, temperature difference and case material.Due to make inner annular housing by the material of selected low linear expansion coefficient and supply in cavity high temperature, high pressure pressurized air and make the thermal expansion more of outside circular shell, thus the interference of the internal face of moving vane front end 61 and inner annular housing 63 can be suppressed.
Further, the internal face of the exhaust side of inner annular housing 63 imposes can grind coating processing be also effective.Can grind coating is by carrying out moltenly penetrating coating, even if make the rotation of moving vane and interfere with the internal face of housing also can easily cut coating portion thus the damage suppressing moving vane on the internal face of housing.By forming two different housings in inner side and outer side, internal side body imposes and can grind coating processing and become easy, effective to reducing costs.
In the present embodiment, the high temperature of being bled from the cavity 65 in downstream side by pipe arrangement 71 of bleeding, high-pressure air are used in the blade cooling of turbo machine, and wherein a part is supplied to the cavity of upstream side.Therefore, it is possible to the air of high temperature, high pressure is imported cavity 64 simply to be formed.Further, with passing through pressurized air can not to be made externally to discharge as the sealing air of the bearing of gas turbine the air of the cavity 64 of upstream side effectively at gas turbine inner utilization heat.
By adopting formation as above, even if moving vane front end 61 and inner walls face also can be avoided to interfere to carrying out spraying droplets during specified running in the present embodiment, the reliability of axial flow compressor can be guaranteed.In addition, because no matter moving vane front space can both be adjusted to suitable gap with or without spraying droplets, so the efficiency of compressor improves, and then the efficiency of gas turbine can be improved.
Next, the compressor of Fig. 3 to the second embodiment of the present invention is used to be described.Fig. 3 is the synoptic diagram in the meridian plane cross section of compressor, be with the difference of the first embodiment shown in Fig. 2, to the air that cavity 64 supplies high temperature, high-pressure air uses axial flow compressor to discharge of the surrounding of encirclement intergrade moving vane 57, and be provided with the passage 73 that can supply this discharge air.By utilizing discharge air as illustrated in fig. 3, become large, therefore, it is possible to the air supply amount of small flow adjustment moving vane front space amount due to during air than the cavity 65 of the downstream stage of supply Fig. 2 of the temperature difference of the metal temperature of outside circular shell 62 and the air of supply.
Here, as the effective structure of bleeding of the discharge air to compressor, be described for high humility gas turbine engine systems.High humility gas turbine is made up of compressor, burner, turbo machine, damping device and regenerative heat exchanger, in the air-breathing of compressor, by air-breathing spraying nozzle, water is generated wet air to air-atomizing.The wet air generated by air-breathing spraying is by compressor compresses, and the bleeder hole that the pressurized air formed by compressor is arranged at the discharge of compressor is once all taken away.The high-pressure air of bleeding from compressor is discharged collaborates in a pipe arrangement, and by damping device humidification.
Supplied to by the regenerative heat exchanger overheated due to the exhaust from turbo machine by the wet air of damping device humidification.Then, in regenerative heat exchanger, overheated from the wet air of damping device supply, supply to burner.The wet air that is supplied to burner burns with fuel mix in burner.Then, the combustion gas of generation make to carry out rotary actuation to turbo machine.The exhaust of discharging from turbo machine is reproduced heat exchanger heat recovery and discharges as exhaust.
Owing to the thermal energy of exhaust can be recovered in combustion air in regenerative heat exchanger, therefore reduce the fuel flow rate of burner and improve the efficiency of gas turbine cycle.In addition, in damping device, humidity is added and under increasing the effect of action fluid, the output of high humility gas turbine increases.Further, under the effect of the effect increased at the effect that makes the temperature of action fluid decline and flow because adding humidity, the heat recovery amount of regenerative heat exchanger increases, the efficiency raising of high humility gas turbine.
In such a system, as mentioned above, there is the structure of all being bled by the air that compressor is discharged.Therefore, be easy to constructively arrange once bleed after to supply the path of a part of high temperature air from a pipe arrangement to cavity.That is, even if will passage 73 be inserted in existing system, also there is no need existing system construction is changed significantly, the system of the reliability continuing existing system can be formed.
Here, the extraction flow of compressor is described.When being 100% making the suction air quantity of compressor, the air being used for bearing seal from compressor is 1 ~ 2%, is about 3 ~ 5% from the blade cooling air of turbine vane sheet side supply.Then, be the about 2wt%(mass fraction sucking air quantity in air-breathing spray amount) time, the metal temperature forming the outside circular shell of the cavity of Fig. 3 reaches about about 120 DEG C.In addition, because the discharged air temperature of compressor reaches about about 400 DEG C, so supply the air of about 400 DEG C to cavity.Discharge air to cavity supply is about 1%, and the thermal expansion amount of housing is approximately 0.3 ~ 0.5mm.The air quantity supplied from this discharge air to cavity is small relative to main flow, in addition, air to cavity supply contributes to being attached to the warming-up of housing, being attached to the evaporation of the drop of wall, subsequently, because bearing seal air can be used as by flowing, so think less on the efficiency reduction impact of gas turbine.
Next, use Fig. 4, the compressor of the third embodiment of the present invention is described.Fig. 4 is the synoptic diagram in the meridian plane cross section of compressor, be with the difference of Fig. 2, directly formed from the mode being communicated with passage 74 supply being arranged at 2 cavitys of inner annular housing from the cavity 65 of downstream stage with the high temperature supplied to the cavity 64 of the surrounding surrounding intergrade moving vane 57, high-pressure air.This passage 74(intercommunicating pore) be the structure that inner annular housing 63 arranges multiple hole vertically.
Although the warming-up effect of the outside circular shell 62 of the present embodiment is the same with Fig. 2, by air supply passage is arranged at inner annular housing 63 in the present embodiment, there is the advantage that pipe arrangement can be made to simplify.But, even if under the operating condition not having air-breathing to spray, owing to supplying high temperature, high-pressure air from downstream side cavity directly to upstream side cavity by pressure difference, be therefore difficult to adjust moving vane front space according to the presence or absence of air-breathing spraying.
In addition, in the present embodiment, as the structure arranging intercommunicating pore on the housing parts across cavity 64 and cavity 65, although supposition arranges the situation of intercommunicating pore as passage 74 on inner annular housing 63, also intercommunicating pore can be set on periphery side body 62 as passage 74.
Next, the compressor of Fig. 5 to the fourth embodiment of the present invention is used to be described.Fig. 5 is the pie graph of the control system of the present embodiment, is, is provided with the difference of the first embodiment shown in Fig. 2: be arranged at the valve 81 supplying the passage of drop to spraying droplets mouth 32; Be arranged at the valve 82 of passage of the cavity supply high temperature to intergrade, high-pressure air; And the vane nose gap sensor 83 of moving vane front space being positioned at and terminating the intergrade of level upstream side than the drop evaporation of compressor can be measured, and possesses the measured value that receives vane nose gap sensor 83 and with the control gear 84 of this measured value control valve 81 and valve 82.
Gap width reducing when measuring moving vane front space, reducing by making the spray amount of drop and can reduce the drop amount being attached to inner annular housing 63, thus the interference in moving vane front end 61 and inner walls face can be suppressed.In addition, when moving vane front space reduces, by supplying high temperature, high-pressure air to cavity 64, can warming-up be carried out to outer ring shape housing 62 and make the standardization of moving vane front space.The reliability of compressor during spraying droplets can be guaranteed thus.
In addition, in the present embodiment, although be the formation of control two valves, the control of side's valve is only used also can to realize effect of the present invention.But, control moving vane front space compared to the action of the valve 81 according to spraying droplets, enable the valve 82 supplying high temperature air to cavity 64 carry out action in shorter time internal control braking vane nose gap.
In addition, in the present embodiment, although the situation passage 72 illustrated in the first embodiment being arranged to the unit of adjust flux is described, the unit arranging adjust flux at the passage 73 of second embodiment's explanation or the passage 74 of the 3rd embodiment explanation also can carry out same control.
Finally, the compressor of Fig. 6 to the fifth embodiment of the present invention is used to be described.Be with the difference of the method for controlling of operation of the 4th embodiment using Fig. 5 to illustrate, the sensor for measuring temperature 85 that inner annular housing 63 is provided as temperature measurement unit replaces the sensor measuring moving vane front space, predicts moving vane front space according to the temperature of compressor inside and the metal temperature measurement of inner annular housing 63.Be prepared in advance in the present embodiment and estimate the prediction type of moving vane front space according to main flow temperature and casing metal temperature 85 in advance, and according to temperature measurement result presumption moving vane front space, make the valve 81 of spraying droplets carry out action and control spray amount.
The present embodiment be that the sensor for measuring temperature 85 of representative is more cheap than moving vane front space sensor with thermocouple.Therefore, due to can be multiple to measure multiple point axially arranging of compressor under same cost, there is the advantage that can improve measuring accuracy., when measuring main flow temperature, at the large drop of the particle diameter of compressor internal flow while being attached to housing, the possibility that drop is also attached to sensor for measuring temperature 85 is higher.As sensor being attached with drop, then thermometric error change is large.Especially, owing to considering that the drop being attached to housing is piled up in the lower half side of housing under gravity, therefore preferably sensor for measuring temperature is arranged at the upper half side of housing.In addition, be also necessary to supply the sealing air for suppressing drop to adhere to.
In addition, although not shown, even if but when controlling to be supplied to high temperature, the high pressure air flow of cavity 64 by the valve etc. be arranged to the passage 72 ~ 74 of cavity supply high-pressure air when replacing the control of the valve 81 of spraying droplets, the object of the present embodiment also can be realized.In addition, as mentioned above, when control to be supplied to the high temperature of cavity 64, high-pressure air flow, can in shorter time internal control braking vane nose gap.
Claims (12)
1. an axial flow compressor, consist of, possess the drop feed unit to the action fluid supply drop of compressor and the housing forming the runner flowed down for above-mentioned stream of action body, and there is multiple to be arranged by continuous print moving vane and a stator blade arranges the level formed, above-mentioned drop evaporates in above-mentioned compressor, the feature of above-mentioned axial flow compressor is
Above-mentioned housing has cavity,
Above-mentioned cavity is by outside housing and surround surrounding that multistage above-mentioned moving vane arranges and side body is formed in the runner that inside forms above-mentioned action fluid,
Possess runner, this runner is used for the above-mentioned action fluid of side farther downstream, the region of the above-mentioned cavity of formation than above-mentioned interior side body to be supplied to above-mentioned cavity.
2. axial flow compressor according to claim 1, is characterized in that,
As for the above-mentioned runner to above-mentioned cavity supply action fluid, there is the runner of the action fluid that supply is extracted out from the centre grade of above-mentioned compressor.
3. axial flow compressor according to claim 1, is characterized in that,
As for the above-mentioned runner to above-mentioned cavity supply action fluid, there is the runner of the action fluid that supply is discharged from above-mentioned compressor.
4. axial flow compressor according to claim 1, is characterized in that,
The downstream side cavity making to flow into than the above-mentioned action fluid of the side farther downstream, region of the above-mentioned cavity of formation of above-mentioned interior side body is possessed in the downstream side of above-mentioned cavity,
As for the above-mentioned runner to above-mentioned cavity supply action fluid, above-mentioned outside housing or interior side body have the intercommunicating pore being communicated with above-mentioned cavity and above-mentioned downstream side cavity.
5. axial flow compressor according to claim 1, is characterized in that,
The material of above-mentioned interior side body is lower than the linear expansion coeffcient of the material of above-mentioned outside housing.
6. axial flow compressor according to claim 1, is characterized in that,
Possesses the unit of the flow regulating the action fluid supplied to above-mentioned cavity.
7. axial flow compressor according to claim 1, is characterized in that,
Possesses the unit of the flow regulating the drop supplied to above-mentioned stream of action body by above-mentioned drop feed unit.
8. axial flow compressor according to claim 6, is characterized in that,
Possess:
The measuring unit in the gap between the inner peripheral surface of above-mentioned interior side body and the front end of multistage above-mentioned moving vane arranged with surrounding by this inner peripheral surface can be measured; And
Control gear, the measured value in the above-mentioned gap that this control gear is measured based on above-mentioned measuring unit, at least one party of the unit of the flow of the drop that the unit of the flow of the action fluid that regulating and controlling supplies to above-mentioned cavity and adjustment supply to above-mentioned stream of action body.
9. axial flow compressor according to claim 6, is characterized in that,
Above-mentioned interior side body possesses the temperature measurement unit for measuring tempeature,
This axial flow compressor possesses control gear, the temperature that this control gear is measured based on said temperature measuring unit, estimate the gap between the inner peripheral surface of above-mentioned interior side body and the front end of multistage above-mentioned moving vane arranged with surrounding by this inner peripheral surface, and at least one party of the unit of the unit of the flow of action fluid that supplies to above-mentioned cavity of regulating and controlling and flow from the drop to above-mentioned stream of action body supply that regulate.
10. axial flow compressor according to claim 2, is characterized in that,
The above-mentioned runner supplying the action fluid extracted out from the centre grade of above-mentioned compressor is runner cooling being supplied to above-mentioned cavity by a part for the turbo machine cooling-air of the turbo machine of the combustion gases drive of high temperature.
11. axial flow compressors according to claim 1, is characterized in that,
Impose in the inner circumferential side of above-mentioned interior side body and can grind coating processing.
The method of operation of 12. 1 kinds of axial flow compressors, the action fluid that this axial flow compressor possesses to compressor supplies the drop feed unit of drop and forms the housing of the runner flowed down for above-mentioned stream of action body, and there is multiple to be arranged by continuous print moving vane and a stator blade arranges the level formed, above-mentioned drop evaporates in above-mentioned compressor, this axial flow compressor has cavity on above-mentioned housing, above-mentioned cavity by outside housing and surround multistage above-mentioned moving vane surrounding and in the runner that inside forms above-mentioned action fluid side body formed, possesses the runner for the above-mentioned action fluid of side farther downstream, the region of the above-mentioned cavity of formation than above-mentioned interior side body being supplied to above-mentioned cavity, the feature of the method for operation of above-mentioned axial flow compressor is,
Measure or estimate the gap between the inner peripheral surface of above-mentioned interior side body and the front end of multistage above-mentioned moving vane arranged with surrounding by this inner peripheral surface, and according to measuring or the above-mentioned gap of presumption, regulate the flow of the action fluid supplied to above-mentioned cavity or to either party in the flow of the drop of above-mentioned stream of action body supply.
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| JP2012281944A JP6092613B2 (en) | 2012-12-26 | 2012-12-26 | Axial flow compressor and operation method of axial flow compressor |
| JP2012-281944 | 2012-12-26 |
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| JP5539131B2 (en) * | 2010-09-14 | 2014-07-02 | 株式会社日立製作所 | Internal bleed structure of 2-shaft gas turbine |
| WO2014189574A2 (en) * | 2013-03-13 | 2014-11-27 | United Technologies Corporation | Variable vane control system |
| FR3024179B1 (en) * | 2014-07-25 | 2016-08-26 | Snecma | PRESSURIZED AIR SUPPLY SYSTEM INSTALLED IN AN AIRCRAFT TURBOMACHINE HAVING SEALING MEANS |
| JP6492737B2 (en) * | 2015-02-19 | 2019-04-03 | 中国電力株式会社 | Gas turbine and gas turbine control method |
| JP5778369B1 (en) * | 2015-05-13 | 2015-09-16 | 隆逸 小林 | Method for producing and using high-density air |
| US10677164B2 (en) * | 2016-11-15 | 2020-06-09 | General Electric Company | Cooling system for a turbine engine |
| JP7173897B2 (en) * | 2019-02-28 | 2022-11-16 | 三菱重工業株式会社 | Gas turbine operating method and gas turbine |
| CN112065774B (en) * | 2020-09-15 | 2022-06-03 | 中国航发沈阳发动机研究所 | Cartridge receiver structure and rotor-stator structure thereof |
| WO2022182730A1 (en) * | 2021-02-23 | 2022-09-01 | Stellar Energy Americas, Inc. | Turbine inlet air cooling systems with condensate water recovery |
| CN113803274B (en) * | 2021-11-19 | 2022-03-04 | 中国航发上海商用航空发动机制造有限责任公司 | Axial compressor and turbofan engine |
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| US20140178176A1 (en) | 2014-06-26 |
| CN103899419A (en) | 2014-07-02 |
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| JP6092613B2 (en) | 2017-03-08 |
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